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guidance and Ignition Control of Lateral-Jet-Controlled Interceptor Missiles

JOURNAL OF guidance CONTROL AND DYNAMICS 2015年第12期38卷 2455-+页

作者： Liu, Lijun Zhu, Chunhui Yu, Zhen Dowell, Earl H. Xiamen Univ Dept Automat Xiamen 361005 Fujian Peoples R China Xiamen Univ Dept Elect Sci Xiamen 361005 Fujian Peoples R China Duke Univ Dept Mech Engn & Mat Sci Durham NC 27708 USA

The guidance and ignition control strategies of lateral-jet-controlled interceptor missiles are proposed based on capture region. The system states keeping inside the capture region will lead to a successful interception. The designs of the non-ignition region enhance the robustness to cope with maneuvering targets. Then, the new ignition control strategies are presented based on dealing with the limitations of the missile dynamic time, the measurement noise, and the shrinking rate of non-ignition region. It is shown that the lateral jet with the fixed acceleration consumes a little more fuel than that with continuously variable accelerations. The main method consumes less fuel than the simple method because of the variable k and the non-ignition region. The results also reveal that the lateral jet can cope with target maneuvering.

关键词： Interceptor Missile guidance Laws terminal guidance Fuel Consumption Model Predictive Control terminal High Altitude Area Defense Tactical Ballistic Missile Projectiles Pulse Jet Jet Fuel

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Sliding mode control based guidance law with impact angle constraint

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Chinese Journal of Aeronautics 2014年第1期27卷 145-152页

作者： Zhao Yao Sheng Yongzhi Liu Xiangdong School of Automation Beijing Institute of Technology Key Laboratory for Intelligent Control & Decision of Complex Systems Beijing Institute of Technology

The terminal guidance problem for an unpowered lifting reentry vehicle against a sta- tionary target is considered. In addition to attacking the target with high accuracy, the vehicle is also expected to achieve a desired impact angle. In this paper, a sliding mode control （SMC）-based guidance law is developed to satisfy the terminal angle constraint. Firstly, a specific sliding mode function is designed, and the terminal requirements can be achieved by enforcing both the sliding mode function and its derivative to zero at the end of the flight. Then, a backstepping approach is used to ensure the finite-time reaching phase of the sliding mode and the analytic expression of the control effort can be obtained. The trajectories generated by this method only depend on the initial and terminal conditions of the terminal phase and the instantaneous states of the vehicle. In order to test the performance of the proposed guidance law in practical application, numerical simulations are carried out by taking all the aerodynamic parameters into consideration. The effec- tiveness of the proposed guidance law is verified by the simulation results in various scenarios.

关键词： Backstepping Impact angle Sliding mode control terminal guidance Unpowered lifting reentryvehicle

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Application of linear gauss pseudospectral method in model predictive control

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ACTA ASTRONAUTICA 2014年第1期96卷 175-187页

作者： Yang, Liang Zhou, Hao Chen, Wanchun Beihang Univ Sch Astronaut Beijing 100191 Peoples R China

This paper presents a model predictive control(MPC) method aimed at solving the nonlinear optimal control problem with hard terminal constraints and quadratic performance index. The method combines the philosophies of the nonlinear approximation model predictive control, linear quadrature optimal control and Gauss Pseudospectral method. The current control is obtained by successively solving linear algebraic equations transferred from the original problem via linearization and the Gauss Pseudospectral method. It is not only of high computational efficiency since it does not need to solve nonlinear programming problem, but also of high accuracy though there are a few discrete points. Therefore, this method is suitable for on-board applications. A design of terminal impact with a specified direction is carried out to evaluate the performance of this method. Augmented PN guidance law in the three-dimensional coordinate system is applied to produce the initial guess. And various cases for target with straight-line movements are employed to demonstrate the applicability in different impact angles. Moreover, performance of the proposed method is also assessed by comparison with other guidance laws. Simulation results indicate that this method is not only of high computational efficiency and accuracy, but also applicable in the framework of guidance design. (C) 2013 IAA. Published by Elsevier Ltd. All rights reserved.

关键词： Linear gauss pseudospectral method Model predictive control Linear quadrature optimal control terminal guidance

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Finite-time Convergent guidance and Control Based on Integrated Model

Finite-time Convergent Guidance and Control Based on Integra...

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26th Chinese Control and Decision Conference (CCDC)

作者： Lin, Lin Wang, Songyan Chao, Tao Yang, Ming Harbin Inst Technol Control & Simulat Ctr Harbin 150001 Peoples R China

ISBN: (纸本)9781479937066

An integrated guidance and control model for missile control system design is established in this paper. Finite-time stability theory is used to design a finite-time convergent guidance and control law based on the proposed model. Some simulation tests are done to verify the validity of the control law designed in this paper and the advantages compared with other guidance laws. The results show the control designed in this paper can satisfy the terminal indicators accurately.

关键词： finite-time convergence control the integrated model terminal guidance

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Finite time L_1 Approach for Missile Overload Requirement Analysis in terminal guidance

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Chinese Journal of Aeronautics 2009年第4期22卷 413-418页

作者： Ji Denggao,He Fenghua,Yao Yu Control and Simulation Center,Harbin Institute of Technology,Harbin 150080,China [a]Control and Simulation Center Harbin Institute of Technology Harbin 150080 China

This article analyzes the problem about the missile overload requirement in a homing terminal guidance under various engagement scenarios. An augmented proportional navigation guidance （APNG） model is introduced on the basis of linear kinematics. To analyze the peak-to-peak performance of the terminal guidance system, a new finite time L1 performance measure for a linear time-varying （LTV） continuous system is proposed. Then, according to the idea of the adjoint system, a novel method for computing the L1 norm of a linear continuous system is first derived. Within the finite time L1 framework, the quantitative relation between the guidance loop dynamics and the maximum missile-target maneuver ratio is offered. This relation is expressed in the form of graphs and formulas that can be used to synthesize some of the major subsystem specifications for the missile guidance system. The illustrative examples show that a significant performance improvement is achieved with the proposed guidance loop dynamics.

关键词： finite time Lx-induced norm performance time varying systems missile overload requirement terminal guidance

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Input-output finite-time stabilization of linear systems with finite-time boundedness

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ISA TRANSACTIONS 2014年第4期53卷 977-982页

作者： Guo, Yang Yao, Yu Wang, Shicheng Ma, Kemao Liu, Kai Guo, Jian Xian Res Inst High Tech Dept Res Xian 710025 Peoples R China Harbin Inst Technol Control & Simulat Ctr Harbin 150080 Peoples R China

The paper presents linear system Input-Output Finite-Time Stabilization (IO-FTS) method under Finite-Time Boundedness (FTB) constraint. A state feedback controller is designed, via Linear Matrix Inequalities (LMIs), to guarantee the system both IO-FTS and FTB. The proposed methods are applied to the guidance design of a class of terminal guidance systems to suppress disturbances with IO-FTS method and FTB constraints simultaneously satisfied. The simulation results illustrate the effectiveness of the proposed methods. (c) 2014 ISA. Published by Elsevier Ltd. All rights reserved.

关键词： Linear system Input-output stability Finite-time bounded Linear matrix inequalities terminal guidance

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A Fuzzy Optimal Sliding-Mode guidance for Intercepting Problem

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IFAC Proceedings Volumes 2014年第3期47卷 3401-3406页

作者： Zhiwei Hou Mao Su Yongji Wang Lei Liu School of Automation Key Laboratory of Ministry of Education for Image Processing and Intelligent Control Huazhong University of Science and Technology Wuhan China

In this paper, a novel terminal guidance law is proposed to solve the problem of exo-atmospheric interception. It is designed based on the proportional navigation (PN) and the classical optimal sliding-mode guidance (OSMG). It overcomes the shortcoming of these two traditional guidance laws and inherits their merits. Particularly, in the scenario of exoatmospheric interception, when the maneuvering information of the targets are unavailable , the proposed guidance law has superior performance than the traditional guidance law. Briefly, to enhance the interceptive performance, we introduce the optimal control and sliding-mode control methods to the guidance law for maneuvering target's interception. On the other hand, the traditional proportional navigation law is introduced to intercept the target with a constant speed. After that, a fuzzy switching function is provided to harmonize both situations above, according to the real-time estimation of maneuver. To guarantee the stability of the law, a Lyapunov based condition is obtained. Finally, different from the two-dimensional simulation in most of the literatures of terminal guidance law researches, we illustrate our method in the nonlinear discrete three-dimensional simulation environment by the Runge-Kutta method. Compared with the pure OSMG and PN, the proposed law performs better.

关键词： terminal guidance Optimal control Sliding-mode control Fuzzy control Lyapunov stability

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Technology Readiness for Hypersonic Vehicles.

Technology Readiness for Hypersonic Vehicles.

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作者： SCIENTIFIC ADVISORY BOARD (AIR FORCE) WASHINGTON DC LOGISTICS CROSS-MATRIX PANEL Department of the Air Force Washington DC SCIENTIFIC ADVISORY BOARD (AIR FORCE) WASHINGTON DC

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Bias-Shaping Method for Biased Proportional Navigation with terminal-Angle Constraint

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JOURNAL OF guidance CONTROL AND DYNAMICS 2013年第6期36卷 1815-1820页

作者： Kim, Tae-Hun Park, Bong-Gyun Tahk, Min-Jea Agcy Def Dev Taejon 305600 South Korea LIG Nexl PGM R&D Lab Songnam 463400 South Korea Korea Adv Inst Sci & Technol Dept Aerosp Engn Taejon 305701 South Korea

The proposed suboptimal guidance with a terminal body-attitude constraint for reentry vehicles in appears to be the first attempt to design an impact-angle-constrained guidance. In a modified proportional navigation (PN) guidance with a time-varying bias, which is a function of relative range, was proposed using a nonlinear planar engagement and Lyapunov-like function. Although various guidance laws to control the impact angle have been developed so far, most of these laws are difficult to implement, especially for a passive homing missile equipped with an infrared seeker, because an accurate time-to-go estimation or range information is required. Thereafter, BPN with zero bias is implemented during the remaining flight because the bias is no longer needed. The proposed shaping method provides valuable features. First, the method does not require a time-to-go estimation and range information. Second, the method has a simple and feasible structure for implementation because only the line-of-sight rate information is required.

关键词： Proportional Navigation guidance Laws Flight Path Angle Angle of Attack Homing Missile Newton Raphson Method Antitank Missiles terminal guidance Reentry Vehicles Missile Dynamics

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Damage Effectiveness Research for terminal Guided Projectile to Armored Target Paper

Damage Effectiveness Research for Terminal Guided Projectile...

引用

International Conference on Quality, Reliability, Risk, Maintenance, and Safety Engineering

作者： Zhao, Zhining Shi, Quan Mi, Dong Dong, Junjie Tang, Jian Feng, Xinhua Liu, Han Ma, Guojiang Ordnance Engn Coll Dept 6 Shijiazhuang Peoples R China Acad Equipment Co Postgrad Management Beijing Peoples R China Bethune Med NOC Coll Shijiazhuang Peoples R China Nanjing Artillery Acad Nanjing Jiangsu Peoples R China Artillery Training Base Gen Staff Zhangjiakou Peoples R China

ISBN: (纸本)9781479910144

To solve the problem of damage effectiveness for terminal guided projectile to armored target, the projectile explosive process based on ANSYS/LY-DYNA program was simulated, and the fragment velocity was found. The penetrating process was simulated when the velocity and quality of the fragment was different, and it shown that some fragments could penetrate the 5cm thickness steel armor. After contrasting the weak parts of the armored target, results indicated that the terminal guided projectile can damage most of the armored target, which may make the loss of combat effectiveness.

关键词： terminal guidance LS-DYNA fragment armored target damage

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